Referece Area of 2D Airfoil
can somebody tell me how the reference area is determined in OF 1.5? Until now I used the chordlength * mesh-extrusion in z direction. But I am not sure as my calculated Cd and Cl values are defnitely wrong.
to avoid any misunderstanding: Th question could also be for which area OF does calculate the forces? (2D)
My impression was that openfoam calculates the forces on all faces of the object and vector sums them. Then divides the drag vector and lift vectors by density, U^2 and the reference area that you specified to get Cd and Cl.
I believe chord_length * wing_length is the standard equation for wing reference area.
For objects other than wings, the reference area for drag is usually the area that the wind 'sees', but when it comes to wings, its the same area as for lift.
I don't think it's your reference_area that's wrong, I think it's the forces coming out of the simulation
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